EP0500458A1 - Verfahren zur Herstellung einer hohlen Schauffel für eine Turbomaschine - Google Patents

Verfahren zur Herstellung einer hohlen Schauffel für eine Turbomaschine Download PDF

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Publication number
EP0500458A1
EP0500458A1 EP92400435A EP92400435A EP0500458A1 EP 0500458 A1 EP0500458 A1 EP 0500458A1 EP 92400435 A EP92400435 A EP 92400435A EP 92400435 A EP92400435 A EP 92400435A EP 0500458 A1 EP0500458 A1 EP 0500458A1
Authority
EP
European Patent Office
Prior art keywords
central
manufacturing
sheets
sheet
hollow blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP92400435A
Other languages
English (en)
French (fr)
Other versions
EP0500458B1 (de
Inventor
André Claude Félix Collot
Bernard Philippe Cornil Sohier
Danilo Varela
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0500458A1 publication Critical patent/EP0500458A1/de
Application granted granted Critical
Publication of EP0500458B1 publication Critical patent/EP0500458B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/053—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure characterised by the material of the blanks
    • B21D26/055—Blanks having super-plastic properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D53/00—Making other particular articles
    • B21D53/78—Making other particular articles propeller blades; turbine blades

Definitions

  • the present invention relates to a method of manufacturing a hollow blade for a turbomachine.
  • FR-A-1 577 388 gives an exemplary embodiment of a blade made up of two wall elements between which is disposed a honeycomb structure, these wall elements being made in particular of titanium alloy and being formed in profile and to the desired shape by hot pressing.
  • FR-A-2 286 688 and FR-A-2 304 438 is a process for producing a metal structure from several parts comprising a superplasticity forming operation, at high temperature, by applying the pressure d '' an inert fluid in a suitable tool, associated with diffusion welding.
  • the object of the invention is to apply to the production of parts having a structure with at least three sheets and having if necessary a controlled distribution of the masses with respect to a centrifugal field in the case of rotating parts, an alternative method of process making it possible in particular to obtain fan blades with a large cord.
  • a single central sheet or two central sheets can be used.
  • the outer sheets can be obtained by hot forming from parts with decreasing thickness or by forming / discharge using methods known per se of hot matrix forging or isothermal forging.
  • the central sheet (s) can be chemically machined, either at the primary part stage in stage (a) of the process, or after stage (b) before the diffusion barriers are put in place.
  • Figure 1 shows an example of two outer sheets 1 equipped with pins 2, and d 'a central sheet 7 constituting the primary parts of the blade.
  • the method of manufacturing these primary parts uses techniques known per se.
  • Figure 1 shows said parts 1 and 7 after a bending / twisting operation according to a known technique of hot forming using a tool not shown in the drawings.
  • a chemical machining operation can be carried out on the central sheet 7 in order to obtain on the blade a determined distribution of the masses by controlling the thicknesses.
  • FIGS. 3A and 3B represent said sheet 7 after chemical machining by showing sections in a direction perpendicular to the edges of the blade to be obtained or in a direction parallel to these edges.
  • Said central sheet 7 is then coated with diffusion barriers delimiting the welding zones 12, as shown in FIG. 4.
  • the application zones of the diffusion barriers are delimited using a mask which can be either a tool rigid or flexible, or an adherent deposit on the surface of a suitable material known per se, which will be cut or peeled, constituting a diffusion barrier during welding and unmasking.
  • Figure 6 shows schematically the establishment of the blade vane 11 on a tool 14 which includes inlets 15 for pressurizing gas and suitable sealing devices.
  • the seal between inside and outside of the tool is produced by a separate seal 16 and the seal between the inside of the blade and the inside of the tool is ensured by means of a peripheral weld of the part, as indicated in 13 in FIG. 5.
  • the seals, on the one hand, of the tool relative to the outside and, on the other hand, the inside of the blade relative to the inside of the tool can be provided using a seal produced directly by creep and welding-diffusion of the outside contour of the part. In this case, the seal footprint will be eliminated during finishing by machining.
  • the welding-diffusion operation is carried out in the oven.
  • the operation is carried out at a temperature of 930 ° C. and a neutral gas, such as argon, is used to obtain pressurization of the parts as shown schematically by the arrows 17.
  • a neutral gas such as argon
  • the pressure applied is 4 MPa.
  • the welds 18 between the central sheet 7 and the external sheets 1 are arranged alternately on one side and the other, as shown in FIG. 6.
  • the blade 11 is then held in place on the single tool 14 to carry out the inflation operation and superplastic forming under argon pressure using the gas collector which has been previously put in place and the gas inlets arranged during of the previous chemical machining operation of the central sheet 7 and during the installation of the blade 11 on the tool 14.
  • the blade 11 during this operation thus takes its final internal shape as shown in figure 7.
  • two central sheets can be used so as to obtain a blade structure as shown diagrammatically in section in FIG. 8 where the external sheets 1 are associated with two central sheets 19 and 20.
  • other structures can be sought as shown in FIG. 9.
  • an operation of inflation under gas pressure and superplastic forming is also applied, in accordance with the invention, after the assembly has been subjected to a bending / twisting operation.
  • the proposed solution optionally makes it possible to use a different material for the central sheets and for the outer sheets, the material of which may, in particular, not have the same superplasticity properties as that of the central sheets.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19920400435 1991-02-20 1992-02-19 Verfahren zur Herstellung einer hohlen Schauffel für eine Turbomaschine Expired - Lifetime EP0500458B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9102007A FR2672826B1 (fr) 1991-02-20 1991-02-20 Procede de fabrication d'une aube creuse pour turbomachine.
FR9102007 1991-02-20

Publications (2)

Publication Number Publication Date
EP0500458A1 true EP0500458A1 (de) 1992-08-26
EP0500458B1 EP0500458B1 (de) 1995-10-04

Family

ID=9409907

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19920400435 Expired - Lifetime EP0500458B1 (de) 1991-02-20 1992-02-19 Verfahren zur Herstellung einer hohlen Schauffel für eine Turbomaschine

Country Status (4)

Country Link
EP (1) EP0500458B1 (de)
JP (1) JP2574589B2 (de)
DE (1) DE69205187T2 (de)
FR (1) FR2672826B1 (de)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0549172A1 (de) * 1991-12-09 1993-06-30 General Electric Company Entwurf und Verfahren zur Herstellung von Hohlschaufeln (drei-Stücke Konzept)
US5469618A (en) * 1993-12-06 1995-11-28 General Electric Company Method for manufacturing hollow airfoils (two-piece concept)
FR2724127A1 (fr) * 1994-09-07 1996-03-08 Snecma Procede de fabrication d'une aube creuse de turbomachine
FR2739045A1 (fr) * 1995-09-27 1997-03-28 Snecma Procede de fabrication d'une aube creuse de turbomachine
WO1997013683A1 (fr) * 1995-10-12 1997-04-17 Aerospatiale Societe Nationale Industrielle Structure metallique creuse monobloc et dissymetrique telle qu'un bord de fuite d'un bec d'attaque d'une voilure d'aeronef et son procede de fabrication
EP0824048A1 (de) * 1996-08-14 1998-02-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zum Herstellen einer hohlen Turbinenschaufel mit Trennmaterial nach dem Schweissen
GB2450934A (en) * 2007-07-13 2009-01-14 Rolls Royce Plc A component with a damping filler
EP2147731A1 (de) * 2008-07-24 2010-01-27 Rolls-Royce plc Schaufel und Verfahren zur Herstellung solcher Schaufel
EP2273069A3 (de) * 2009-07-02 2011-10-12 Rolls-Royce plc Verfahren zum Bilden einer inneren Struktur in einer Hohlkomponente
US20110274555A1 (en) * 2009-01-22 2011-11-10 Ihi Corporation Production method of leading edge reinforcement of fan blade
US8241004B2 (en) 2008-05-15 2012-08-14 Rolls-Royce, Plc Component structure
US8365388B2 (en) 2009-01-28 2013-02-05 Rolls-Royce Plc Method of joining plates of material to form a structure
US8701286B2 (en) 2010-06-02 2014-04-22 Rolls-Royce Plc Rotationally balancing a rotating part
US8920893B2 (en) 2009-01-27 2014-12-30 Rolls-Royce Plc Article with an internal structure
US8986490B2 (en) 2010-11-26 2015-03-24 Rolls-Royce Plc Method of manufacturing a component
CN105263649A (zh) * 2013-06-12 2016-01-20 三菱重工业株式会社 板状工件的扭转保持装置、扭转保持方法及扭转成形方法

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0522121D0 (en) * 2005-10-29 2005-12-07 Rolls Royce Plc A blade
EP1832714A1 (de) * 2006-03-06 2007-09-12 Siemens Aktiengesellschaft Verfahren zur Herstellung einer Turbinen- oder Verdichterkomponente sowie Turbinen- oder Verdichterkomponente
KR100843448B1 (ko) * 2007-03-20 2008-07-03 현대중공업 주식회사 진동 감쇄형 익형 날개
CN101827682B (zh) * 2007-09-19 2014-07-02 巴恩斯集团 扩散粘结
CN113523728B (zh) * 2021-08-04 2023-01-03 哈尔滨汽轮机厂有限责任公司 一种空心导叶片的特种加工方法
CN113857346B (zh) * 2021-09-26 2024-01-09 北京航空航天大学 一种空心叶片热成型方法及空心叶片充气装置

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0245548A1 (de) * 1985-04-15 1987-11-19 Ontario Technologies Corporation Herstellungsverfahren für eine hohle Metallstruktur vom Typ einer Tragfläche
US4882823A (en) * 1988-01-27 1989-11-28 Ontario Technologies Corp. Superplastic forming diffusion bonding process
FR2647373A1 (fr) * 1989-05-26 1990-11-30 Dassault Avions Procede de formage par deformation par pression de fluide

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0245548A1 (de) * 1985-04-15 1987-11-19 Ontario Technologies Corporation Herstellungsverfahren für eine hohle Metallstruktur vom Typ einer Tragfläche
US4882823A (en) * 1988-01-27 1989-11-28 Ontario Technologies Corp. Superplastic forming diffusion bonding process
FR2647373A1 (fr) * 1989-05-26 1990-11-30 Dassault Avions Procede de formage par deformation par pression de fluide

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
SHEET METAL INDUSTRIES. vol. 66, no. 10, Octobre 1989, REDHILL GB pages 507 - 511; R. PEARCE: 'Advanced Sheet Metal Technologie for the Aerospace Industry' *

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0549172A1 (de) * 1991-12-09 1993-06-30 General Electric Company Entwurf und Verfahren zur Herstellung von Hohlschaufeln (drei-Stücke Konzept)
US5469618A (en) * 1993-12-06 1995-11-28 General Electric Company Method for manufacturing hollow airfoils (two-piece concept)
FR2724127A1 (fr) * 1994-09-07 1996-03-08 Snecma Procede de fabrication d'une aube creuse de turbomachine
EP0700738A1 (de) 1994-09-07 1996-03-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Turbinenschaufel
US5826332A (en) * 1995-09-27 1998-10-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Method and manufacturing a hollow turbomachine blade
FR2739045A1 (fr) * 1995-09-27 1997-03-28 Snecma Procede de fabrication d'une aube creuse de turbomachine
EP0765711A1 (de) * 1995-09-27 1997-04-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung einer hohlen Turbinenschaufel
WO1997013683A1 (fr) * 1995-10-12 1997-04-17 Aerospatiale Societe Nationale Industrielle Structure metallique creuse monobloc et dissymetrique telle qu'un bord de fuite d'un bec d'attaque d'une voilure d'aeronef et son procede de fabrication
FR2739832A1 (fr) * 1995-10-12 1997-04-18 Aerospatiale Structure metallique creuse monobloc et dissymetrique telle qu'un bord de fuite d'un bec d'attaque d'une voilure d'aeronef et son procede de fabrication
EP0824048A1 (de) * 1996-08-14 1998-02-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zum Herstellen einer hohlen Turbinenschaufel mit Trennmaterial nach dem Schweissen
FR2752388A1 (fr) * 1996-08-14 1998-02-20 Snecma Procede de fabrication d'une aube creuse de turbomachine comportant un decollement apres soudage
US5946802A (en) * 1996-08-14 1999-09-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Process for the manufacture of a hollow turbomachine blade and apparatus for use in said process
GB2450934A (en) * 2007-07-13 2009-01-14 Rolls Royce Plc A component with a damping filler
GB2450934B (en) * 2007-07-13 2009-10-07 Rolls Royce Plc A Component with a damping filler
US8857054B2 (en) 2007-07-13 2014-10-14 Rolls-Royce Plc Method of forming an aerofoil with a damping filler
US8381398B2 (en) 2007-07-13 2013-02-26 Rolls-Royce Plc Component with a damping filler and method
US8182233B2 (en) 2007-07-13 2012-05-22 Rolls-Royce Plc Component with a damping filler
US8241004B2 (en) 2008-05-15 2012-08-14 Rolls-Royce, Plc Component structure
EP2147731A1 (de) * 2008-07-24 2010-01-27 Rolls-Royce plc Schaufel und Verfahren zur Herstellung solcher Schaufel
US8529720B2 (en) 2008-07-24 2013-09-10 Rolls-Royce, Plc Aerofoil sub-assembly, an aerofoil and a method of making an aerofoil
US20110274555A1 (en) * 2009-01-22 2011-11-10 Ihi Corporation Production method of leading edge reinforcement of fan blade
US9289816B2 (en) * 2009-01-22 2016-03-22 Ihi Corporation Production method of leading edge reinforcement of fan blade
US8920893B2 (en) 2009-01-27 2014-12-30 Rolls-Royce Plc Article with an internal structure
US8365388B2 (en) 2009-01-28 2013-02-05 Rolls-Royce Plc Method of joining plates of material to form a structure
EP2273069A3 (de) * 2009-07-02 2011-10-12 Rolls-Royce plc Verfahren zum Bilden einer inneren Struktur in einer Hohlkomponente
US8701286B2 (en) 2010-06-02 2014-04-22 Rolls-Royce Plc Rotationally balancing a rotating part
US8986490B2 (en) 2010-11-26 2015-03-24 Rolls-Royce Plc Method of manufacturing a component
CN105263649A (zh) * 2013-06-12 2016-01-20 三菱重工业株式会社 板状工件的扭转保持装置、扭转保持方法及扭转成形方法
CN105263649B (zh) * 2013-06-12 2017-05-31 三菱重工业株式会社 板状工件的扭转保持装置、扭转保持方法及扭转成形方法
US9789526B2 (en) 2013-06-12 2017-10-17 Mitsubishi Heavy Industries, Ltd. Plate-like-workpiece twisting and retaining apparatus, plate-like-workpiece twisting and retaining method, and plate-like-workpiece twisting and shaping method

Also Published As

Publication number Publication date
FR2672826B1 (fr) 1995-04-21
EP0500458B1 (de) 1995-10-04
JP2574589B2 (ja) 1997-01-22
JPH05192729A (ja) 1993-08-03
DE69205187T2 (de) 1996-04-04
FR2672826A1 (fr) 1992-08-21
DE69205187D1 (de) 1995-11-09

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